EP3867145B1 - Hinge fairing - Google Patents

Hinge fairing Download PDF

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Publication number
EP3867145B1
EP3867145B1 EP19816439.4A EP19816439A EP3867145B1 EP 3867145 B1 EP3867145 B1 EP 3867145B1 EP 19816439 A EP19816439 A EP 19816439A EP 3867145 B1 EP3867145 B1 EP 3867145B1
Authority
EP
European Patent Office
Prior art keywords
wing
fairing
aircraft
tip device
flight
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP19816439.4A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP3867145A1 (en
Inventor
Richard Lowry
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Operations Ltd
Original Assignee
Airbus Operations Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Airbus Operations Ltd filed Critical Airbus Operations Ltd
Publication of EP3867145A1 publication Critical patent/EP3867145A1/en
Application granted granted Critical
Publication of EP3867145B1 publication Critical patent/EP3867145B1/en
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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
    • B64C23/06—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices
    • B64C23/065—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices at the wing tips
    • B64C23/069—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices at the wing tips using one or more wing tip airfoil devices, e.g. winglets, splines, wing tip fences or raked wingtips
    • B64C23/072—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices at the wing tips using one or more wing tip airfoil devices, e.g. winglets, splines, wing tip fences or raked wingtips the wing tip airfoil devices being moveable in their entirety
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/38—Adjustment of complete wings or parts thereof
    • B64C3/54—Varying in area
    • B64C3/546—Varying in area by foldable elements
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C7/00—Structures or fairings not otherwise provided for
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/38—Adjustment of complete wings or parts thereof
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/38—Adjustment of complete wings or parts thereof
    • B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/10—Drag reduction

Definitions

  • folding wing tip devices have been introduced into passenger aircraft, where a wing tip device is movable between a flight configuration for use during flight, and a ground configuration for use during ground-based operations. In the ground configuration, the wing tip device is moved away from the flight configuration such that the span of the aircraft wing is reduced, thereby allowing use of existing gates and safe taxiway usage.
  • the folding wing tip device may be connected to a fixed wing via a hinge arrangement.
  • the hinge arrangement may protrude beyond the wing skin of the fixed wing and wing tip device, resulting in a need for a fairing to cover the exposed section of the hinge arrangement in order that the aerodynamic performance of the wing is not adversely affected.
  • Various shapes of fairings are already known on an aircraft, for example blister fairings or flap track fairings.
  • locating already-known shapes of fairing at the junction between the folding wing tip device and fixed wing have been found to result in an undesirable degree of lift loss and/or additional drag, when compared to a non-folding wing of the same span.
  • CN105438443 discloses a folding wing that can be used to change the aerodynamic area of an aircraft wing and save space.
  • the mechanism comprises an inner wing section, an outer wing section, and a conformal rotating body which extends beyond both the leading edge and trailing edge of the wing.
  • the present invention seeks to mitigate the above-mentioned problems. Alternatively or additionally, the present invention seeks to provide an improved fairing to reduce or eliminate the impact on lift loss at a junction between a fixed wing and wing tip device.
  • the present invention provides an aircraft wing comprising a fixed wing and a wing tip device at the tip thereof, wherein the wing tip device is configurable between: (i) a flight configuration for use during flight and (ii) a ground configuration for use during ground-based operations, in which ground configuration the wing tip device is rotated away from the flight configuration about a hinge axis such that the span of the aircraft wing is reduced, the aircraft wing further comprising a hinge arrangement connecting the fixed wing and the wing tip device, wherein the hinge arrangement protrudes beyond an outer surface of the fixed wing and wing tip device, and a fairing covering the protruding portion of the hinge, wherein in the flight configuration the fairing comprises a front portion blended into and extending rearwardly from the leading edge of the fixed wing and the wing tip device and the front portion of the fairing (18) meets the leading edge of the fixed wing and wing tip device in a tangential direction, such that when viewed in a line of flight direction cross-section, there is no discontinu
  • Provision of a fairing with a front portion blended into the leading edge of the fixed wing and wing tip device has been found to be especially aerodynamically efficient. For example, compared to the use of other fairing shapes, it may reduce or eliminate the lift loss experienced by an aircraft wing where the fixed wing and wing tip device meet.
  • the blending of the fairing into the leading edge of the fixed wing and wing tip device means that there are no discontinuities between the fairing and the leading edge of the fixed wing and wing tip device. This blending is in all directions, so tracing a line across the fairing and the leading edge of the fixed wing and wing tip device in a span-wise direction, a smooth transition is provided. Equally, tracing a line backwards from the leading edge of the fixed wing and wing tip device in a line of flight direction, a smooth transition is provided.
  • the front portion of the fairing may be considered as aerodynamically seamless where it blends with the leading edge of the wing, such that the shape of the fairing results in no separation or stagnation points being created by the front portion of the fairing when the aircraft is in flight.
  • There may be a line of continuous curvature extending from the front portion of the fairing around the leading edge of the wing.
  • the line of continuous curvature may extend around the fairing and the wing in a line of flight direction.
  • the fairing may be shaped such that the depth of the fairing is greatest to correspond with the maximum protrusion of the hinge arrangement.
  • the fairing may comprise a concave surface from the wing skin of the fixed wing, the concave surface starting in a direction substantially tangential to the wing skin.
  • the fairing may further comprise a point of inflection in a span-wise direction, at which point the surface becomes a convex surface, such that the convex surface peaks to correspond to the maximum protrusion of the hinge arrangement.
  • the fairing may further comprise an additional point of inflection, at which point the surface becomes a concave surface, such that the concave surface meets the wing tip device wing skin in a substantially tangential direction. This applies when the wing tip device is in the flight configuration, not necessarily when the wing tip device is in the ground configuration.
  • the bell-shaped profile may be very small, or non-existent (i.e. flat) because the fairing blends with the leading edge of the wing, but as the front portion extends rearwardly from the leading edge, the depth of the bell-shaped profile may increase.
  • the aircraft may comprise one or more seals where the fairing meets the fixed wing and/or the wing tip device
  • the fairing may be substantially symmetrical about a chord-wise axis, running along the line of flight direction, the axis located at the point of greatest depth of the fairing.
  • the fairing may be symmetrical about such a chord-wise axis along at least 70%, 80% or 90% of the axis. If the wing is a swept wing, the very front of the front portion of the fairing may deviate from symmetry due to the angle created between the leading edge of the fixed wing and wing tip device and the axis. If the wing is a swept wing, a rear portion of the fairing may deviate from symmetry due to the angle created by the trailing edge of the fairing and the axis.
  • the edges of the fairing, where the fairing blends into the fixed wing or wing tip device may extend in a line of flight direction.
  • the fairing may have a consistent width in a span-wise direction. Such an arrangement may improve suction and reduce lift loss.
  • the front portion of the fairing meets the leading edge of the fixed wing and wing tip device in a tangential direction, such that when viewed in a line of flight direction cross-section, there is no discontinuity between the fairing and the leading edge of the fixed wing and wing tip device.
  • the hinge arrangement may extend in a line of flight direction.
  • the hinge arrangement may extend in a line of flight direction such that it extends over at least 60%, at least 70%, at least 80%, or at least 90% of the chord of the aircraft wing in a line of flight direction (i.e. between the leading edge of the wing and the trailing edge of the wing in a line of flight direction).
  • the hinge arrangement may protrude from at or near the leading edge of the fixed wing and wing tip device.
  • the present invention provides a fairing which enables the hinge arrangement in such an aircraft wing to be covered without it being necessary to extend the fairing beyond the leading edge of the aircraft wing. Such an arrangement may be advantageous aerodynamically.
  • the fairing may be located on the bottom surface of the aircraft wing.
  • the lower surface of the aircraft wing is defined as the surface of the wing which faces the ground when the aircraft is on the ground.
  • the fairing may be located on the upper surface of the wing. The determination of the surface with which to associate the fairing may depend on the surface from which the hinge arrangement protrudes.
  • the fairing may further comprise a rear portion with a concave surface in a line of flight direction, the surface creating a lift-generating portion of the fairing during flight.
  • Shaping the fairing such that a portion acts as a lift-generating portion during flight may eliminate or reduce the lift loss typically associated with the placement of a fairing on an aircraft wing.
  • the rear portion may comprise a trailing edge with a width in the span-wise direction.
  • the rear portion may extend beyond the trailing edge of the fixed wing and wing tip device.
  • the rear portion of the fairing may comprise a trailing edge which is parallel to the trailing edge of the fixed wing and/or wing tip device.
  • the rear portion may taper in span-wise width as it extends away from the trailing edge of the fixed wing and wing tip device.
  • the rear portion may comprise a point of inflection in the line of flight direction, at which point the cross-sectional profile of the rear portion in the line of flight direction changes from a convex profile to a concave profile, as the rear portion extends in a rearward direction.
  • the point of inflection may be located in a region around the 100%, 90%, 80%, 70%, or 60% of the chord length of the wing, taken in a line of flight direction and moving from the leading edge (0%) to trailing edge (100%) of the wing.
  • the line of flight direction is taken along the longitudinal axis of the aircraft.
  • the span-wise direction is taken to be perpendicular to the line of flight direction.
  • the aircraft may be arranged such that as the fairing extends in a span-wise direction, the rear portion of the fairing comprises a surface which extends substantially tangentially from the wing skin of the fixed wing in a concave direction, undergoes a point of inflection to extend in a convex direction, and undergoes a further point of inflection such that it extends in a concave direction to a point where it is substantially tangential to the wing skin of the wing tip device.
  • This bell-shaped cross-section may reduce in depth as the rear portion extends rearwardly, such that at the trailing edge of the fairing, the bell-shaped cross-section is much reduced or eliminated (i.e. flat) in a span-wise direction.
  • the aircraft may comprise one or more seals where the fairing meets the fixed wing and/or the wing tip device.
  • the invention provides an aircraft comprising the aircraft wing of the first aspect.
  • an aircraft comprising an aerodynamic structure and a fairing, wherein the fairing is blended into the aerodynamic structure in a line of flight direction and a span-wise direction, such that there are no discontinuities in the transition from the aerodynamic structure and the fairing.
  • the fairing may comprise a point of inflection in a line of flight direction. Such a point of inflection may improve the aerodynamic performance of the fairing.
  • the fairing may add to the lift created by the aerodynamic structure.
  • the wing tip device is configurable between: (a) a flight configuration for use during flight and (b) a ground configuration for use during ground-based operations, in which ground configuration the wing tip device is moved away from the flight configuration such that the span of the aircraft wing is reduced.
  • the span In the flight configuration, the span may exceed an airport compatibility limit.
  • the span In the ground configuration the span may be reduced such that the span (with the wing tip device in the ground configuration) is less than, or substantially equal to, the airport compatibility limit.
  • the airport compatibility limit is a span limit (for example relating to clearance restrictions for buildings, signs, other aircraft).
  • the compatibility limit is preferably a gate limit.
  • the wing tip device may be a wing tip extension; for example the wing tip device may be a planar tip extension.
  • the wing tip device may comprise, or consist of, a non-planar device, such as a winglet.
  • the trailing edge of the wing tip device is preferably a continuation of the trailing edge of the fixed wing.
  • the leading edge of the wing tip device is preferably a continuation of the leading edge of the fixed wing.
  • the upper and the lower surfaces of the wing tip device may be continuations of the upper and lower surfaces of the fixed wing.
  • the span ratio of the fixed wing relative to the wing tip device may be such that the fixed wing comprises at least 70%, 80%, 90%, or more, of the overall span of the aircraft wing.
  • the aircraft incorporating the wing may be unsuitable for flight.
  • the wing tip device may be aerodynamically and/or structurally unsuitable for flight in the ground configuration.
  • the aircraft is preferably configured such that, during flight, the wing tip device is not moveable to the ground configuration.
  • the aircraft may comprise a sensor for sensing when the aircraft is in flight. When the sensor senses that the aircraft is in flight, a control system is preferably arranged to disable the possibility of moving the wing tip device to the ground configuration.
  • the aircraft is preferably a passenger aircraft.
  • the passenger aircraft preferably comprises a passenger cabin comprising a plurality of rows and columns of seat units for accommodating a multiplicity of passengers.
  • the aircraft may have a capacity of at least 20, more preferably at least 50 passengers, and more preferably more than 50 passengers.
  • the aircraft is preferably a powered aircraft.
  • the aircraft preferably comprises an engine for propelling the aircraft.
  • the aircraft may comprise wing-mounted, and preferably underwing, engines.
  • Figure 1 shows an aircraft wing 10 comprising a wing tip device 12 and a fixed wing 14.
  • the wing tip device 12 is in a ground configuration in which the span of the aircraft wing 10 is reduced compared to a flight configuration.
  • Figure 2 shows the aircraft wing 10 of figure 1 as part of an aircraft 100.
  • the aircraft wing 100 is in the flight configuration, where the wing tip device 12 has been extended from the ground configuration shown in figure 1 .
  • Figures 3 and 4 show an enlarged schematic view of the wing tip device 12, fixed wing 14, and a fairing 18 which extends from the wing tip device 12 to the fixed wing 14 when the aircraft is in the flight configuration.
  • Figure 6 shows a cross-sectional slice of a middle section of the wing 10 in a span-wise direction.
  • the wing tip device 12 is connected to the fixed wing 14 via a hinge arrangement 16.
  • the hinge arrangement 16 extends from a position at or close to the leading edge of the wing 10 to a position at or close to the trailing edge of the wing 10.
  • the protruding structure may take a number of forms depending on the design of the hinge arrangement.
  • the hinge may include lugs, locking mechanisms, and/or actuation mechanisms, at least part of which may protrude from the wing outer mould line (OML). In most cases it is expected that at least part of the hinge arrangement for a folding wing tip.
  • OML wing outer mould line
  • the hinge arrangement 16 allows the folding upwards, along a hinge line 22, of the wing tip device 12 from the flight configuration shown in figure 2 to the ground configuration shown in figure 1 .
  • the folding of the wing tip device between the flight configuration and ground configuration is controlled by an actuator (not shown) which may form part of the hinge arrangement 16.
  • the hinge arrangement 16 may also comprise a locking mechanism arranged to lock the folding wing tip device into the flight configuration. Various different locking mechanism may be suitable, as would be understood by a skilled person. As such, no further details will be provided.
  • the hinge arrangement 16 extends outside the wing skin envelope of the fixed wing 14 and the folding wing tip 12, in particular extending from the underside of the wing 10.
  • Figure 7 shows an second cross-sectional view of the arrangement of figure 6 , the cross-sectional view taken in the line of flight direction and through the hinge line 22.
  • the outer surface of the fairing 18 is represented by a dashed line, which extends beyond the lower wing skin of the fixed wing 14 and wing tip device 12 to cover the hinge 16. Further details about the shape of the fairing are provided below
  • FIG. 5 shows the underside of the wing 10 and fairing 18 which covers the hinge arrangement 16.
  • the fairing 18 comprises a front portion 20 which is blended into and extends rearwardly from the leading edge 23 of the fixed wing 14 and wing tip device 12.
  • the hinge arrangement 16 comprises a hinge line 22 which is aligned with the line of flight direction.
  • the fairing 18 is also aligned with the line of flight direction and approximately symmetrical about the hinge axis 22.
  • the span-wise edges of the fairing also extend in a line of flight direction, such that the span-wise width of the fairing is consistent. Providing parallel, line of flight oriented, edges to the fairing 16 acts to maintain lift due to the existence of the fairing, giving a continuity of span loading.
  • the blending of the front portion 20 of the fairing 18 into the leading edge 23 of the fixed wing 14 and folding wing tip device 12 means that, when looking a cross section of the wing profile in the line of flight direction (as in figure 7 ), there are no discontinuities or abrupt edges as the profile is traced from the leading edge 23 towards the trailing edge of the wing 10. As shown in Figure 7 , a line traced from the upper surface of the wing 10, around the leading edge 23, and rearwards along the front portion of the fairing has a continuous curvature.
  • the cross sectional shape traced by the fairing 18 in the span-wise direction is bell shaped, so the fairing 18 initially extends from the wing skin of the fixed wing 14 in a concave manner, undergoes a point of inflection and extends in a convex manner as it extends around the hinge arrangement 16, undergoes a further point of inflection and extends in a concave manner to the wing skin of the folded wing tip device 12. At the point where the fairing 18 meets the wing skin of the fixed wing 14 and folding wing tip device 12, the fairing 18 extends substantially tangentially to the wing skin.
  • the fairing 18 also comprises a rear portion 24, which extends beyond the trailing edge of the fixed wing 14 and folding wing tip device 12 in a rearward direction.
  • the rear portion 24 tapers in width as it extends beyond the trailing edge of the fixed wing 14 and folding wing tip device 12.
  • the rear portion 24 comprises a trailing edge 26, which is approximately aligned with the trailing edge of the fixed wing 14 and folding wing tip device 12.
  • the point of inflection 21 when the fairing extends far enough beyond the trailing edge of the wing 10, the point of inflection 21 may be located around 110%, 120% or more of the chord length of the wing.
  • the exact location of the point of inflection 21 may depend on the particular wing and hinge configuration, and be determined experimentally, by testing how the variation in location affects the lift loss experienced as a result of introduction of the fairing 18.
  • Figure 10 shows a three-dimensional representation of the fairing (similar to figure 3 ) with the point of inflection 21 clearly indicated with a line showing how the surface changes direction.
  • Figures 8 and 9 show a similar fairing and wing arrangement to that shown in figures 3 to 7 , and 10 .
  • a wing tip device 12' and a fixed wing 14' are joined by a hinge (not shown) and a fairing 18' covers the hinge where it protrudes from the OML of the wing.
  • the front portion of the fairing 18' is the same shape as in the first embodiment described.
  • the rear portion of the fairing 18' is the same shape as in the first embodiment described, in that the rear portion comprises a surface which creates a concave surface.
  • the fairing 18' does not extend beyond the trailing edge of the wing 10'. Such an arrangement may be possible when the protrusion of the hinge joining the fixed wing 14' and the wing tip device 12' is reduced either in depth or in the line of flight direction.
  • Figure 11 shows a schematic representation of a graph showing the lift characteristics of a wing as it extends in a span-wise direction.
  • the hinge line and the wing tip are indicated on the span axis of the graph.
  • Figure 12 shows an expanded section 600 of the graph shown in figure 11 .
  • conventional fairings as indicated by the lines 606, for example blister shaped fairings, result in lift loss in the part of the wing to which they are attached.
  • the blended fairing as described above, is lift-neutral when compared to a fixed wing with no wing tip device and associated fairing.
  • the lift characteristics of a wing without a fairing is shown by line 602 and the lift characteristics of the wing according to an embodiment of the invention is shown by line 604. Therefore, it can be seen the present invention offers significant advantages of the existing fairing designs.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Toys (AREA)
EP19816439.4A 2019-01-30 2019-12-02 Hinge fairing Active EP3867145B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB1901268.1A GB2581136A (en) 2019-01-30 2019-01-30 Hinge fairing
PCT/GB2019/053399 WO2020157446A1 (en) 2019-01-30 2019-12-02 Hinge fairing

Publications (2)

Publication Number Publication Date
EP3867145A1 EP3867145A1 (en) 2021-08-25
EP3867145B1 true EP3867145B1 (en) 2024-05-22

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP19816439.4A Active EP3867145B1 (en) 2019-01-30 2019-12-02 Hinge fairing

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US (1) US11840328B2 (zh)
EP (1) EP3867145B1 (zh)
CN (1) CN113165731B (zh)
GB (1) GB2581136A (zh)
WO (1) WO2020157446A1 (zh)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2580930A (en) * 2019-01-30 2020-08-05 Airbus Operations Ltd Fairing for folding wing tip

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB934286A (en) * 1961-06-16 1963-08-14 English Electric Co Ltd Improvements in and relating to wing tip folding mechanisms

Family Cites Families (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB504747A (en) * 1937-10-30 1939-05-01 Vickers Aviat Ltd Improvements in or connected with aircraft engine cowlings
GB574361A (en) * 1943-06-01 1946-01-02 Fairey Aviat Co Ltd Improvements in or relating to folding wing aircraft
US2881994A (en) * 1953-11-09 1959-04-14 Northrop Aircraft Inc Convex panel wing construction
US2925233A (en) * 1957-02-18 1960-02-16 Chance Vought Aircraft Inc Aircraft wing fold system
FR1320450A (fr) * 1962-04-19 1963-03-08 English Electric Co Ltd Mécanisme de pliage d'une extrémité d'aile sur les avions
US5427329A (en) * 1992-01-30 1995-06-27 The Boeing Company Locking hydraulic latch pin actuator
US5381986A (en) 1992-01-30 1995-01-17 The Boeing Company Folding wing-tip system
US9027883B2 (en) * 2008-11-05 2015-05-12 Airbus Operations Limited Aircraft fairing
US8272594B2 (en) * 2009-10-26 2012-09-25 Aerion Corporation Laminar flow wing optimized for supersonic cruise aircraft
US9469392B2 (en) * 2012-10-30 2016-10-18 The Boeing Company Wing fold system rotating latch
GB201220854D0 (en) * 2012-11-20 2013-01-02 Airbus Operations Ltd Retractable infill panel for high-lift device
US9616995B2 (en) * 2012-12-13 2017-04-11 Stoprotor Technology Pty Ltd Aircraft and methods for operating an aircraft
GB201301680D0 (en) 2013-01-31 2013-03-13 Airbus Uk Ltd Downwardly extending wing tip device
US9452825B2 (en) 2013-04-19 2016-09-27 The Boeing Company Winglet attach fitting for attaching a split winglet to a wing
GB2524827A (en) * 2014-04-04 2015-10-07 Airbus Operations Ltd A passenger aircraft with a downwardly foldable wing tip device
GB2535489A (en) * 2015-02-17 2016-08-24 Airbus Operations Ltd An arrangement for moving a wing tip device between a flight configuration and a ground configuration
FR3037560B1 (fr) * 2015-06-16 2018-06-01 Airbus Operations Aile d'aeronef comprenant un embout d'aile pilotable en incidence
CN105438443B (zh) * 2015-12-08 2017-11-21 中国航空工业集团公司成都飞机设计研究所 一种保形折叠翼
US10259566B1 (en) * 2016-06-13 2019-04-16 James Randolph Lawrence Rolling vortex wing slat system and method of use
CN106184711B (zh) * 2016-09-28 2018-04-03 西北工业大学 变体飞机的机翼折叠机构
GB2557978A (en) * 2016-12-21 2018-07-04 Airbus Operations Ltd Locking device
GB2567899A (en) * 2017-10-31 2019-05-01 Airbus Operations Ltd Aircraft wing and wing tip device with fairing
BR112020018688A2 (pt) * 2018-03-12 2020-12-29 Aero Design Labs, Inc. Método para fabricar uma carenagem de asa ao corpo e carenagem de asa ao corpo
GB2580930A (en) * 2019-01-30 2020-08-05 Airbus Operations Ltd Fairing for folding wing tip

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB934286A (en) * 1961-06-16 1963-08-14 English Electric Co Ltd Improvements in and relating to wing tip folding mechanisms

Also Published As

Publication number Publication date
GB2581136A (en) 2020-08-12
GB201901268D0 (en) 2019-03-20
US11840328B2 (en) 2023-12-12
CN113165731B (zh) 2024-08-27
WO2020157446A1 (en) 2020-08-06
EP3867145A1 (en) 2021-08-25
US20220009619A1 (en) 2022-01-13
CN113165731A (zh) 2021-07-23

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